PILOT'S OPERATING' HANDBOOK and FAA APPROVED AIRPLANE FLIGHT MANUAL

a listing of all pages in the handbook. Pages affected by the current revision are indicated by an asterisk (*) preceding the pages listed. LOG OF EFFECTIVE PAGES Dates of issue for original and revised pages are: Original 1 October 1978 Page Date Page 6-2 Blank... . 1 6-3 ihru 6-13 1 6-14 Blank 1 6-15 thru 6-25 1 6-26 Blank 1 7-1 thru 7-49 1 7-50 Blank 1 8-1 1 8-2 Blank . 8-3 thru 8-15 1 8-16 Blank 1 9-1 thru 9-2 1 Date October 1978 October 1978 October 1978 October 1978 October 1978 October 1978 October 1978 October 1978 October 1978 October 1978 October 1978 October 1978 Title 1 October 1978 Assignment Record .. 1 October 1978 i th ru iv , 1 October 1978 1-1 thru 1-9 1 October 1978 1-10 Blank 1 October 1978 2-1 1 October 1978 2-2 Blank 1 October 1978 2-3 thru 2-11 1 October 1978 2-12 Blank 1 October 1978 3-1 thru 3-19 1 October 1978 3-20 Blank 1 October 1978 4-1 thru 4-24 1 October 1978 5-1 , 1 October 1978 5-2 Blank " ., 1 October 1978 5-3 thru 5-29 1 October 1978 5-30 Blank 1 October 1978 6-1 , 1 October 1978 1 October 1978 NOTE Refer to Section 9 Table of Contents for supplements applicable to optional systems. iii TABLE OF CONTENTS CESSNA MODEL TR182 TABLE OF CONTENTS SECTION GENERAL 1 LlMITATIONS 2 EMERGENCY PROCEDURES 3 NORMAL PROCEDURES 4 PERFORMANCE 5 WEIGHT & BALANCE! EQUIPMENT LlST 6 AIRPLANE & SYSTEMS DESCRIPTIONS 7 AIRPLANE HANDLING, SERVICE & MAINTENANCE 8 SUPPLEMENTS (Optional Systems Description & Operating Procedures) 9 iv 1 October 1978 CESSNA MODEL TR182 SECTION 1 GENERAL SECTION 1 GENERAL TABLE OF CONTENTS Page Three View 1-2 Introduction 1-3 Descriptive Data 1-3 Engine 1-3 Propeller 1-3 Fuel . . . 1-3 Oil 1~ Maximum Certificated Weights 1-5 Standard Airplane Weights 1-5 Cabin And Entry Dimensions . 1-5 Baggage Space And Entry Dimensions 1-5 Specific Loadings 1-5 Symbols, Abbreviations And Terminology 1-6 General Airspeed Terminology And Symbols 1-6 Meteorological Terminology 1-7 Engine Power Terminology . . . . . . . . 1-7 Airplane Performance And Flight Planning 'I'errnIno.log'y 1-7 Weight And Balance Terminology . . . . . . . . . . . 1-8 1 October 1978 1-1 SECTION 1 GENERAL CESSNA MODEL TR182 ------.\ L-~-~~--~- 28'_71/2" NOTES: 1. Dimensions shown are based on standard empty weight and proper nose gear and tire inflation. 2. Wing span shown with strobe lights installed. Maximum height shown with nose gear depressed as far as possible and flashing beacon installed. Wheel base length is 65". 5. Propeller ground clearance is 11 1/2". 6. Wing area is 174 square feet. 7. Minimum turning radius (*pivot point to outboard wing tip) is 27'-0", * PIVOT POINT 1-----------------36'-0 ..'------------------1 Figure 1-1. Three View 1-2 1 October 1978 CESSNA MODEL TR182 SECTION,1 GENERAL INTRODUCTION This handbook contains 9 sections, and includes the material required to be furnished to the pilot by CAR Part 3. It also contains supplemental data supplied by Cessna Aircraft Company. Section 1 provides basic data and information of general interest. It also contains definitions or explanations of symbols, abbreviations, and terminology commonly used. DESCRIPTIVE DATA ENGINE Number of Engines: 1. Engine Manufacturer: Avco Lycoming. Engine Model Number: 0-540-L3C5D. Engine Type: Turbocharged, direct-drive, air-cooled, horizontally- opposed, carburetor equipped, six-cylinder engine with 541.5 cu. in. displacemen t. Horsepower Rating and Engine Speed: 235rated BHP at 31 inches Hg and 2400 RPM. PROPELLER Propeller Manufacturer: McCauley Accessory Division. Propeller Model Number: B2D34C217/90DHB-8. Number of Blades: 2. Propeller Diameter, Maximum: 82 inches. Minimum: 80.5 inches. Propeller Type: Constant speed and hydraulically actuated, with a low pitch setting of 15.8°and a high pitch setting of 31.9°(30inch station). FUEL Approved Fuel Grades (and Colors): 100LLGrade Aviation Fuel (Blue). 100 (Formerly 100/130) Grade Aviation Fuel (Green). 1 October 1978 1-3 SECTION 1 GENERAL CESSNA MODELTR182 Total Capacity: 92 gallons. Total Capacity Each Tank: 46 gallons. Total Usable: 88 gallons. NOTE To ensure maximum fuel capacity when refueling and minimize cross-feeding when parked on a sloping surface, place the fuel selector valve in either LEFT or RIGHT position. Oil Oil Grade (Specification): MIL-L-6082 Aviation Grade Straight Mineral Oil: Use to replenish supply during first 25 hours and at the first 25-hour oil change. Continue to use until a total of 50 hours has accumulated or oil consumption has stabilized. NOTE The airplane was delivered from the factory with a corro- sion preventive aircraft engine oil. This oil should be drained after the first 25 hours of operation. MIL-L-22851 Ashless Dispersant Oil: This oil must be used after first 50 hours or oil consumption has stabilized. Recommended Viscosity For Temperature Range: MIL-L-6082 Aviation Grade Straight Mineral Oil: SAE 50 above 16°C (60°F). SAE 40 between -PC (30°F) and 32°C (90°F). SAE 30 between -18°C (O°F) and 21°C (700F). SAE 20 below -12°C (10°F). MIL-L-22851 Ashless Dispersant Oil: SAE 40 or SAE 50 above 16°C (60°F). SAE 40 between -1°C (30°F) and 32°C (90°F). SAE 30 or SAE 40 between -18°C (OaF) and 21°C (70°F). SAE 30 below -12°C (10°F). Oil Capacity: Sump: 8 Quarts. Total: 9 Quarts. 1-4 1 October 1978 CESSNA MODEL TR182 SECTION 1 GENERAL MAXIMUM CERTIFICATED WEIGHTS Ramp: 3112lbs. Takeoff: 3100lbs. Landing: 3100lbs. Weight in Baggage Compartment: Baggage Area" A" (or passenger on child's seat) - Station 82to 110:120 lbs. See note below. Baggage Area "B" - Station 110to 134:80 lbs. See note below. NOTE The maximum combined weight capacity for baggage areas A and B is 200 lbs. STANDARD AIRPLANE WEIGHTS Standard Empty Weight, Turbo Skylane RG: 1764lbs. Turbo Skylane RG II: 1815lbs. Maximum Useful Load, Turbo Skylane RG: 1348lbs. Turbo Skylane RG II: 1297lbs. CABIN AND ENTRY DIMENSIONS Detailed dimensions of the cabin interior and entry door openings are illustrated in Section 6. BAGGAGE SPACE AND ENTRY DIMENSIONS Dimensions of the baggage area and baggage door opening are illustrated in detail in Section 6. SPECIFIC LOADINGS Wing Loading: 17.8Ibs./sq. ft. Power Loading: 13.2lbs./hp. 1 October 1978 1-5 SECTION 1 GENERAL CESSNA MODEL TR182 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS KCAS Knots Calibrated Airspeed is indicated airspeed corrected for position and instrument error and expressed in knots. Knots calibrated airspeed is equal to KT AS in standard atmosphere at sea level. KIAS Knots Indicated Airspeed is the speed shown on the airspeed indicator and expressed in knots. KTAS Knots True Airspeed is the airspeed expressed in knots relative to undisturbed air which is KCAS corrected for altitude and temperature. Manuevering Speed is the maximum speed at which you may use abrupt control travel. Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position. Maximum Landing Gear Extended Speed is the maximum speed at which an airplane can be safely flown with the landing gear extended. Maximum Landing Gear Operating Speed is the maximum speed at which the landing gear can be safely extended or retracted. Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air, then only wi th caution. VNE Never Exceed Speed is the speed limit that may not be exceeded at any time. Stalling Speed or the minimum steady flight speed at which the airplane is controllable. Stalling Speed or the minimum steady flight speed at which the airplane is controllable in the landing configu- ration at the most forward center of gravity. 1-6 1 October 1978 CESSNA MODELTR182 SECTION 1 GENERAL Best Angle-of-Climb Speed is the speed which results in the greatest gain of altitude in a given horizontal distance. Best Rate-of-Climb Speed is the speed which results in the greatest gain in altitude in a given time. OAT METEOROLOGICAL TERMINOLOGY Standard Tempera- ture Pressure Altitude Outside Air Temperature is the free air static temperature. It is expressed in either degrees Celsius or degrees Fah- renheit. Standard Temperature is 15°C at sea level pressure alti- tude and decreases by 2°C for each 1000 feet of altitude. Pressure Altitude is the altitude read from an altimeter when the altimeter's barometric scale has been set to 29.92 inches of mercury (1013 mb). BRP ENGINE POWER TERMINOLOGY Brake Horsepower is the power developed by the engine. RPM MP Revolutions Per Minute is engine speed. Manifold Pressure is a pressure measured in the engine's induction system and is expressed in inches of mercury (Rg). AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Demon- strated Crosswind Velocity Usable Fuel Unusable Fuel GPH 1 October 19'78 Demonstrated Crosswind Velocity is the velocity of the crosswind component for which adequate control of the airplane during takeoff and landing was actually demon- strated during certification tests. The value shown is not considered to be limiting. Usable Fuel is the fuel available for flight planning. Unusable Fuel is the quantity of fuel that can not be safely used in flight. Gallons Per Hour is the amount of fuel (in gallons) consumed per hour. 1-'7 SECTION 1 GENERAL NMPG g CESSNA MODEL TR182 Nautical Miles Per Gallon is the distance (in nautical miles) which can be expected per gallon of fuel consumed at a specific engine power setting and/ or flight configura- tion. g is acceleration due to gravity. WEIGHT AND BALANCE TERMINOLOGY Reference Datum Station Arm Moment Center of Gravity (C.G.) C.G. Arm C.G. Limits Standard Empty Weight Basic Empty Weight Useful Load 1-8 Reference Datum is an imaginary vertical plane from which all horizontal distances are measured for balance purposes. Station is a location along the airplane fuselage given in terms of the distance from the reference datum. Arm is the horizontal distance from the reference datum to the center of gravity (C.G.) of an item. Moment is the product of the weight of an item multiplied by its arm. (Moment divided by the constant 1000is used in this handbook to simplify balance calculations by reduc- ing the number of digits.) Center of Gravity is the point at which an airplane, or equipment, would balance if suspended. Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane. Center of Gravity Arm is the arm obtamed by adding the airplane's individual moments and dividing the sum by the total weight. Center of Gravity Limits are the extreme center of gravity locations within which the airplane must be operated at a given weight. Standard Empty Weight is the weight of a standard air- plane, including unusable fuel, full operating fluids and full engine oil. Basic Empty Weight is the standard empty weight plus the weight of optional equipment. Useful Load is the difference between ramp weight and the basic empty weight. 1 October 1978 CESSNA MODEL TR182 Maximum Ramp Weight Maximum Takeoff Weight Maximum Landing Weight Tare 1 October 1978 SECTION 1 GENERAL Maximum Ramp Weight is the maximum weight approved for ground maneuver. (It includes the weight of start, taxi and run up fuel.) Maximum Takeoff Weight is the maximum weight approved for the start of the takeoff run. Maximum Landing Weight is the maximum weight approved for the landing touchdown. Tare is the weight of chocks, blocks, stands, etc. used when weighing an airplane, and is included in the scale read- ings. Tare is deducted from the scale reading to obtain the actual (net) airplane weight. 1-9/(1-10 blank) CESSNA MOPEL TR182 SECTION 2 LIMITATIONS TABLE OF CONTENTS Introduction . . . . . . . . Airspeed Limitations Airspeed Indicator Markings Power Plant Limitations Power Plant Instrument Markings Weight Limits . . . . . Center Of Gravity Limits . Maneuver Limits Flight Load Factor Limits Kinds Of Operation Limits Fuel Limitations . . . . . Maximum Operating Altitude Limit Other Limitations Flap Limitations Placards ..... 1 October 1978 SECTION 2 LIMIT ATIONS Page 2-3 2-4 2-4 2-5 2-6 2-6 2-7 2-7 2-7 2-7 2-8 2-8 2-8 2-.8 2-9 2-1/(2-2blank) CESSNA MODELTR182 SECTION 2 LIMITATIONS INTRODUCTION Section 2 includes operating limitations, instrument markings, and basic placards necessary for the safe operation of the airplane, its engine, standard systems and standard equipment. The limitations included in this section and in Section 9 have been approved by the Federal Aviation Administration. Observance of these operating limitations is required by Federal Aviation Regulations. NOTE Refer to Section 9 of this Pilot's Operating Handbook for amended operating limitations, operating procedures, performance data and other necessary information for airplanes equipped with specific options. NOTE The airspeeds listed in the Airspeed Limitations chart (figure 2-1) and the Airspeed Indicator Markings chart (figure 2-2) are based on Airspeed Calibration data shown in Section 5 with the normal static source, with the exception of the bottom of the green and white arcs on the airspeed indicator. These are based on a power-off air- speed calibration. If the alternate static source is being used, ample margins should be observed to allow for the airspeed calibration variations between the normal and alternate static sources as shown in Section 5. Your Cessna is certificated under FAA Type Certificate No. 3A13 as Cessna Model No. TR182. 1 October 1978 2-3 SECTION 2 LIMITATIONS CESSNA MODEL TR182 AIRSPEED LIMITATIONS Airspeed limitations and their operational significance are shown in figure 2-1. SPEED KCAS KIAS REMARKS VNE Never Exceed Speed 175 179 Do not exceed this speed in any operation. VNO Maximum Structural 155 157 Do not exceed th is speed Cruising Speed except in smooth air, and then only with caution. VA Maneuvering Speed: 3100 Pounds 111 112 Do not make full or abrupt 2600 Pounds 101 102 control movements above 2100 Pounds 91 91 this speed. VFE Maximum Flap Extended Speed To 100 Flaps 138 140 Do not exceed these speeds 100 - 400 Flaps 97 95 with the given flap settings. VLO Maximum Landing Gear 139 140 Do not extend or retract landing Operating Speed gear above this speed. VLE Maximum Landing Gear 139 140 Do not exceed th is speed with Extended Speed landing gear extended Maximum Window Open 175 179 Do not exceed this speed with Speed windows open. Figure 2-1. Airspeed Limitations AIRSPEED INDICATOR MARKINGS Airspeed indicator markings and their color code significance are shown in figure 2-2. 2-4 1 October 1978 CESSNA MODEL TR182 /// SECTION 2 LIMITATIONS MARKING KIAS VALUE SIGNIFICANCE OR RANGE White Arc 43 - 95 Full Flap Operating Range. Lower limit is maximum weight VSo in landing configuration. Upper limit is maximum speed permissible with flaps extended. Green Arc 43 - 157 Normal Operating Range. Lower limit is maximum weight Vs at most forward C.G. with flaps retracted. Upper limit is maximum structural cruising speed. Yellow Arc 157 - 179 Operations must be conducted with caution and only in smooth air. Red Line 179 Maximum speed for all operations. Figure 2-2. Airspeed Indicator Markings POWER PLANT LIMITATIONS Engine Manufacturer: Avco Lycoming. Engine Model Number: 0-540-L3C5D. Engine Operating Limits for Takeoff and Continuous Operations: Maximum Power: 235 BHP. Maximum Engine Speed: 2400 RPM. Maximum Manifold Pressure: 31 in. Hg. Maximum Cylinder Head Temperature: 500°F (260°C). Maximum Oil Temperature: 245°F (118°C). Oil Pressure, Minimum: 25 psi. Maximum: 100psi. Fuel Pressure, Minimum: 0.5 psi. Maximum: 30.0 psi. Propeller Manufacturer: McCauley Accessory Division. Propeller Model Number: B2D34C217/90DHB-8 Propeller Diameter, Maximum: 82 inches. Minimum: 80.5 inches. Propeller Blade Angle at 30 Inch Station, Low: 15.8°. High: 31.9°. 1 October 1978 2-5 SECTION 2 LIMITATIONS CESSNA MODEL TR182 POWER PLANT INSTRUMENT MARKINGS Power plant instrument markings and their color code significance are shown in figure 2-3. RED LINE GREEN ARC RED LINE INSTRUMENT MINIMUM NORMAL MAXIMUM LIMIT OPERATING LIMIT Tachometer - - - 2100 2400 RPM 2400 RPM Manifold Pressure - - - 17 - 25 31 in. Hg in. Hg Oil Temperature - - - 100° - 245°F 245°F Cylinder Head - - - 200° - 500°F 500°F Temperature Fuel Flow (Pressure) 0.5 psi 0.5 - 30.0 psi 30.0 psi Oil Pressure 25 psi 60 - 90 psi 100 psi Fuel Quantity E - - - - - - (2 Gal. Unusable Each Tank) Suction - - - 4.5 - 5.4 - - - in. Hg Figure 2-3. Power Plant Instrument Markings WEIGHT LIMITS Maximum Ramp Weight: 3112lbs. Maximum Takeoff Weight: 3100lbs. Maximum Landing Weight: 31001bs. Maximum Weight in Baggage Compartment: Baggage Area "A" (or passenger on child's seat) - Station 82to 110:120 Ibs. See note below. Baggage Area "B" - Station 110to 134: 80 lbs. See note below. 2-6 1 October 1978 CESSNA MODEL TR182 SECTION 2 LIMITATIONS NOTE The maximum combined weight capacity for baggage areas A and B is 200 lbs. CENTER OF GRAVITY LIMITS Center of Gravity Range: Forward: 33.0inches aft of datum at 2250lbs. or less, with straight line variation to 35.5inches aft of datum at 2700lbs., with straight line variation to 40.9 inches aft of datum at 3100lbs. Aft: 47.0inches aft of datum at all weights. Moment Change Due To Retracting Landing Gear: +3052lb.-ins. Reference Datum: Front face of firewall. MANEUVER LIMITS This airplane is certificated in the normal category. The normal category is applicable to aircraft intended for non-aerobatic operations. These include any maneuvers incidental to normal flying, stalls (except whip stalls), lazy eights, chandelles, and steep turns in which the angle of bank is not more than 60°. Aerobatic maneuvers, including spins, are not approved. FLIGHT LOAD FACTOR LIMITS Flight Load Factors: *Flaps Up: +3.8g, -1.52g *Flaps Down: t2.0g *The design load factors are 150% of the above, and in all cases, the structure meets or exceeds design loads. KINDS OF OPERATION LIMITS The airplane is equipped for day VFR and may be equipped for night VFR and/or IFR operations. FAR Part 91 establishes the minimum required instrumentation and equipment for these operations. The refer- ence to types of flight operations on the operating limitations placard reflects equipment installed at the time of Airworthiness Certificate issuance. Flight into known icing conditions is prohibited. 1 October 1978 2-7 SECTION 2 LIMITATIONS CESSNA MODEL TR182 FUEL LIMITATIONS 2 Standard Tanks: 46.0U.S. gallons each. Total Fuel: 92.0U.S. gallons. Usable Fuel (all flight conditions): 88 U.S. gallons. Unusable Fuel: 4.0 tr.s. gallons. NOTE To ensure maximum fuel capacity when refueling and minimize cross-feeding when parked on a sloping surface, place the fuel selector valve in either LEFT or RIGHT position. Takeoff and land with the fuel selector valve handle in the BOTHposition. Operation on either left or right tank is limited to level flight only. With 1/4 tank or less, prolonged uncoordinated flight is prohibited when operating on either left or right tank in level flight. Approved Fuel Grades (and Colors): 100LLGrade Aviation Fuel (Blue). 100 (Formerly 100/130) Grade Aviation Fuel (Green). MAXIMUM OPERATING ALTITUDE LIMIT Certificated Maximum Operating Altitude: 20,000Ft. OTHER LIMITATIONS FLAP LIMITATIONS Approved Takeoff Range: 0° to 20°. Approved Landing Range: 0° to 40°. 2-8 1 October 1978 CESSNA MODEL TR182 SECTION 2 LIMITATIONS PLACARDS The following information must be displayed in the form of composite or individual placards. 1. In full view of the pilot: (The "DAY-NIGHT-VFR-IFR" entry, shown on the example below, will vary as the airplane is equipped.) The markings and placards installed in this airplane contain operating limitations which must be complied with when operating this airplane in the Normal Category. Other operat- ing limitations which must be complied with when operating this airplane in this category are contained in the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. No acrobatic maneuvers, including spins, approved. Flight into known icing conditions prohibited. This airplane is certified for the following flight operations as of date of original airworthiness certificate: DAY-NIGHT-VFR-IFR 2. Near airspeed indicator: MAX SPEED - KIAS MANEUVER 112 GEAR OPER 140 GEAR DOWN 140 3. On control lock: CONTROLLOCK - REMOVEBEFORE STARTING ENGINE 1 October 1978 2-9 SECTION 2 LIMITATIONS CESSNA MODEL TR182 4. On the fuel selector valve: OFF LEFT - 44 GAL. LEVEL FLIGHT ONLY BOTH - 88 GAL. ALL FLIGHT ATTITUDES BOTH ON FOR TAKEOFF AND LANDING RIGHT - 44 GAL. LEVEL FLIGHT ONLY 5. On the baggage door: 120 POUNDS MAXIMUM BAGGAGE AND/OR AUXILIARY PASSENGER FORWARD OF BAGGAGE DOOR LATCH AND 80 POUNDS MAXIMUM BAGGAGE AFT OF BAGGAGE DOOR LATCH MAXIMUM 200 POUNDS COMBINED FOR ADDITIONAL LOADING INSTRUCTIONS SEE WEIGHT AND BALANCE DATA 6. On flap position indicator: (Partial flap range with blue color code and 140 kt callout; also, me- chanical detent at 10°.) (Indices at these positions with white color code and 95 kt callout; also, mechanical detent at 10° and 20°.) 10° to 20° FULL 2-10 1 October 1978 CESSNA MODEL TR182 SECTION 2 LIMITATIONS 7. Forward of fuel tank filler cap: FUEL 100LL/100 MIN GRADE AVIATION GASOLINE CAP. 46.0 U.S. GAL. CAP. 34.5 U.S. GAL. TO BOTTOM OF FILLER NECK 8. Near landing gear hand pump: MANUAL GEAR EXTENSION 1. SELECT GEAR DOWN 2. PULL HANDLE FWD 3. PUMP VERTICALLY CAUTION DO NOT PUMP WITH GEAR UP SELECTED 9. A calibration card is provided to indicate the accuracy of the magnetic compass in 30° increments. 10. On oil filler cap: OIL 8 QTS 1 October 1978 2-11/(2-12 blank) CESSNA MODEL TR182 SECTION 3 EMERGENCYPROCEDURES SECTION 3 EMERGENCY PROCEDURES TABLE OF CONTENTS Page Introduction . . . . . . . . . . . . Airspeeds For Emergency Operation . 3-3 . 3-3 OPERATIONAL CHECKLISTS Engine Failures 3-3 Engine Failure During Takeoff Run . . . 3-3 Engine Failure Immediately After Takeoff 3-4 Engine Failure During Flight . . . . . . 3-4 Forced Landings . . . . . . . . . . ... . . 3-4 Emergency Landing Without Engine Power 3-4 Precautionary Landing With Engine Power 3-4 Ditching . . . . . . . . 3-5 Fires . . . . . . . . . . . 3-5 During Start On Ground 3-5 Engine Fire In Flight . 3-6 Electrical Fire In Flight 3-6 Cabin Fire 3-7 Wing Fire . . . . . . 3-7 Icing . . . . . . 3-7 Inadvertent Icing Encounter 3-7 Static Source Blockage (Erroneous Instrument Reading Suspected) . . . . . . . . . 3-8 Landing Gear Malfunction Procedures 3-8 Landing Gear Fails To Retract 3-8 Landing Gear Fails To Extend 3-8 Gear Up Landing . . . . . . . 3-9 Landing Without Positive Indication Of Gear Locking 3-9 Landing With A Defective Nose Gear (Or Flat Nose Tire) 3-9 Landing With A Flat Main Tire . . . . . 3-10 Electrical Power Supply System Malfunctions . . 3-10 Ammeter Shows Excessive Rate of Charge (Full Scale Deflection) 3-10 Low-Voltage Light Illuminates Dur-ing Flight (Ammeter Indicates Discharge) ..... 3-10 1 October 1978 3-1 SECTION 3 EMERGENCY PROCEDURES TABLE OF CONTENTS (Continued) AMPLIFIED PROCEDURES Engine Failure . Forced Landings . Landing Without Elevator Control Fires . . . . . . . . . . . . . Emergency Operation In Clouds (Vacuum System Failure) Executing A 1800 Turn In Clouds Emergency Descent Through Clouds Recovery From A Spiral Dive . . . Inadvertent Flight Into Icing Conditions Static Source Blocked . Spins . Rough Engine Operation Or Loss Of Power Carburetor Icing . . Spark Plug Fouling . Magneto Malfunction . . . . . . Engine-Driven Fuel Pump Failure Low Oil Pressure . . . . . . . . Landing Gear Malfunction Procedures Retraction Malfunctions Extension Malfunctions Gear Up Landing .... Electrical Power Supply System Malfunctions Excessive Rate Of Charge Insufficient Rate Of Charge . . . . . . . 3-2 CESSNA MODEL TR182 Page 3-11 3-12 3-12 3-12 3-13 3-13 3-13 3-14 3-14 3-15 3-15 3-16 3-16 3-16 3-16 3-16 3-17 3-17 3-17 3-18 ·1· 3-18 3-18 3-19 3-19 1 October 1978 CESSNA MODEL TR182 SECTION 3 EMERGENCY PROCEDURES INTRODUCTION Section 3 provides checklist and amplified procedures for coping with emergencies that may occur. Emergencies caused by airplane or engine malfunctions are extremely rare if proper preflight inspections and maintenance are practiced. Enroute weather emergencies can be minim- ized or eliminated by careful flight planning and good judgment when unexpected weather is encountered. However, should an emergency arise, the basic guidelines described in this section should be considered and applied as necessary to correct the problem. Emergency procedures associated with ELT and other optional systems can be found in Section 9. AIRSPEEDS FOR EMERGENCY OPERATION Engine Failure After Takeoff: Wing Flaps Up . . Wing Flaps Down Maneuvering Speed: 3100Lbs 2600Lbs .. 2100Lbs .. Maximum Glide: 3100Lbs 2600Lbs .. 2100Lbs .. Precautionary Landing With Engine Power Landing Without Engine Power: Wing Flaps Up . . Wing Flaps Down 70 KIAS 65 KIAS 112 KIAS 102KIAS 91 KIAS 81 KIAS 74 KIAS 67 KIAS 65 KIAS 75 KIAS 65 KIAS OPERATIONAL CHECKLISTS ENGINE FAILURES ENGINE FAILURE DURING TAKEOFF RUN 1. Throttle -- IDLE. 2. Brakes -- APPLY. 3. Wing Flaps -- RETRACT. 4. Mixture -- IDLE CUT-OFF. 5. Ignition Switch -- OFF. 6. Master Switch -- OFF. 1 October 1978 3-3 SECTION 3 EMERGENCY PROCEDURES CESSNA MODEL TR182 ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF 1. Airspeed -- 70 KIAS (flaps UP). 65 KIAS (flaps DOWN). 2. Mixture -- IDLE CUT-OFF. 3. Fuel Selector Valve -- OFF. 4. Ignition Switch -- OFF. 5. Wing Flaps -- AS REQUIRED (400 recommended). 6. Master Switch -- OFF. ENGINE FAILURE DURING FLIGHT 1. Airspeed -- 80 KIAS. 2. Carburetor Heat -- ON. 3. Fuel Selector Valve -- BOTH 4. Mixture -- RICH. 5. Ignition Switch -- BOTH (or START if propeller is stopped). 6. Primer -- IN and LOCKED. FORCED LANDINGS EMERGENCY LANDING WITHOUT ENGINE POWER 1. Airspeed -- 70 KIAS (flaps UP). 65 KIAS (flaps DOWN). 2. Mixture -- IDLE CUT-OFF. 3. Fuel Selector Valve -- OFF. 4. Ignition Switch •• OFF. 5. Landing Gear -- DOWN (UP if terrain is rough or soft). 6. Wing Flaps -- AS REQUIRED (400 recommended). 7. Doors -- UNLATCH PRIOR TO TOUCHDOWN. 9. Master Switch -- OFF when landing is assured. 10. Touchdown -- SLIGHTLY TAIL LOW. 12. Brakes -- APPLY HEAVILY. PRECAUTIONARY LANDING WITH ENGINE POWER 1. Airspeed -- 65 KIAS. 2. Wing Flaps -- 200• 3. Selected Field -- FLY OVER, noting terrain and obstructions, then retract flaps upon reaching a safe altitude and airspeed. 4. Electrical Switches -- OFF. 5. Landing Gear -- DOWN (UP if terrain is rough or soft). 6. Wing Flaps -- 40° (on final approach). 7. Airspeed -- 65 KIAS. 3-4 1 October 1978 CESSNA MODEL TR182 SECTION 3 EMERGENCY PROCEDURES 8. Doors -- UNLATCH PRIOR TO TOUCHDOWN. 9. Avionics Power and Master Switches -- OFF. 10. Touchdown -- SLIGHTLY TAIL LOW. 11. Ignition Switch -- OFF. 12. Brakes -- APPLY HEAVILY. DITCHING 1. Radio -- TRANSMIT MAYDAY on 121.5MHz. giving location and intentions and SQUAWK 7700 if transponder is installed. 2. Heavy Objects (in baggage area) -- SECURE OR JETTISON. 3. Landing Gear -- UP. 4. Flaps -- 20° - 40°. 5. Power -- ESTABLISH 300 FT/MIN DESCENT at 60 KIAS. 6. Approach -- High Winds, Heavy Seas -- INTO THE WIND. Light Winds, Heavy Swells -- PARALLEL TO SWELLS. NOTE If no power is available, approach at 70KIAS with flaps up or at 65 KIAS with 10° flaps. 7. Cabin Doors -- UNLATCH. 8. Touchdown -- LEVEL ATTITUDE AT ESTABLISHED DESCENT. 9. Face -- CUSHION at touchdown with folded coat. 10. Airplane -- EVACUATE through cabin doors. If necessary, open windows and flood cabin to equalize pressure so doors can be opened. 11. Life Vests and Raft -- INFLATE. FIRES DURING START ON GROUND 1. Cranking -- CONTINUE, to get a start which would suck the flames and accumulated fuel through the carburetor and into the engine. If engine starts: 2. Power -- 1700RPM for a few minutes. 3. Engine -- SHUTDOWN and inspect for damage. If engine fails to start: 4. Throttle -- FULL OPEN. 1 October 1978 3-5 SECTION 3 EMERGENCY PROCEDURES CESSNA MODEL TR182 5. Mixture -- IDLE CUT-OFF. 6. Cranking -- CONTINUE. 7. Fire Extinguisher -- OBTAIN(have ground attendants obtain if not installed). 8. Engine -- SECURE. a. Master Switch -- OFF. b. Ignition Switch -- OFF. c. Fuel Selector Valve -- OFF. 9. Fire -- EXTINGUISH using fire extinguisher, wool blanket, or dirt. 10. Fire Damage -- INSPECT, repair damage or replace damaged components or wiring before conducting another flight. ENGINE FIRE IN FLIGHT 1. Mixture -- IDLE CUT-OFF. 2. Fuel Selector Valve -- OFF. 3. Master Switch -- OFF. 4. Cabin Heat and Air -- OFF (except overhead vents). 5. Airspeed -- 100 KIAS (If fire is not extinguished, increase glide speed to find an airspeed which will provide an incombustible mixture). 6. Forced Landing -- EXECUTE (as described in Emergency Landing Without Engine Power). ELECTRICAL FIRE IN FLIGHT 1. Master Switch -- OFF. 2. Avionics Power Switch -- OFF. 3. All Other Switches (except ignition switch) -- OFF. 4. Vents/Cabin Air/Heat -- CLOSED. 5. Fire Extinguisher -- ACTIVATE (if available). I WARNING I After discharging an extinguisher within a closed cabin, ventilate the cabin. If fire appears out and electrical power is necessary for continuance of flight: 6. Master Switch -- ON. 7. Circuit Breakers -- CHECK for faulty circuit, do not reset. S. Radio Switches -- OFF. 9. Avionics Power Switch -- ON. 10. Radio/Electrical Switches -- ON one at a time, with delay after each until short circuit is localized. 3-6 1 October 1975 CESSNA MODELTR182 SECTION 3 EMERGENCY PROCEDURES 11. Vents/Cabin Air/Heat -- OPEN when it is ascertained that fire is completely extinguished. CABIN FIRE 1. Master Switch -- OFF. 2. Vents/Cabin Air/Heat -- CLOSED (to avoid drafts). 3. Fire Extinguisher -- ACTIVATE (if available). I WARNING I After discharging an extinguisher within a closed cabin, ventilate the cabin. 4. Land the airplane as soon as possible to inspect for damage. WING FIRE 1. Navigation Light Switch •• OFF. 2. Strobe Light Switch (if installed) -- OFF. 3. Pitot Heat Switch (if installed) -- OFF. NOTE Perform a sideslip to keep the flames away from the fuel tank and cabin, and land as soon as possible using flaps only as required for final approach and touchdown. ICING INADVERTENT ICING ENCOUNTER 1. Turn pitot heat switch ON (if installed). 2. Turn back or change altitude to obtain an outside air temperature that is less conducive to icing. 3. Pull cabin heat control full out and rotate defroster control clock" wise to obtain maximum defroster airflow. 4. Increase engine speed to minimize ice build-up on propeller blades. 5. Watch for signs of carburetor air filter ice and apply carburetor heat only as required. An unexplained loss in manifold pressure could be caused by carburetor ice or air intake filter ice. Lean the mixture if carburetor heat is used continuously. 1 October 1978 3-7 SECTION 3 EMERGENCY PROCEDURES CESSNA MODEL TR182 6. Plan a landing at the nearest airport. With an extremely rapid ice build-up, select a suitable "off airport" landing site. 7. With an ice accumulation of 1/4 inch or more on the wing leading edges, be prepared for significantly higher stall speed. 8. Leave wing flaps retracted. With a severe ice build-up on the horizontal tail, the change in wing wake airflow direction caused by wing flap extension could result in a loss of elevator effective- ness. 9. Open the window and, if practical, scrape ice from a portion of the windshield for visibility in the landing approach. 10. Perform a landing approach using a forward slip, if necessary, for improved visibility. 11. Approach at 85 to 95 KIAS, depending upon the amount of ice accumulation. 12. Perform a landing in level attitude. STATiC SOURCE BLOCKAGE (Erroneous Instrument Reading Suspected) 1. Alternate Static Source Valve -- PULL ON. 2. Airspeed -- Consult appropriate table in Section 5. 3. Altitude -- Cruise 50 feet higher and approach 30 feet higher than normal. LANDING GEAR MALFUNCTION PROCEDURES LANDING GEAR FAILS TO RETRACT 1. Master Switch -- ON. 2. Landing Gear Lever -- CHECK (lever full up). 3. Landing Gear and Gear Pump Circuit Breakers -- IN. 4. Gear Up Light -- CHECK. 5. Landing Gear Lever -- RECYCLE. 6. Gear Motor -- CHECK operation (ammeter and noise). LANDING GEAR FAILS TO EXTEND 1. Landing Gear Lever -- DOWN. 2. Emergency Hand Pump -- EXTEND HANDLE, and PUMP (perpen- dicular to handle until resistance becomes heavy -- about 20 cycles). 3. Gear Down Light -- ON. 4. Pump Handle -- STOW. 3-8 1 October 1978 CESSNA MODEL TR182 SECTION 3 EMERGENCY PROCEDURES GEAR UP LANDING 1. Landing Gear Lever -- UP. 2. Landing Gear and Gear Pump Circuit Breakers -- IN. 3. Runway -- SELECT longest hard surface or smooth sod runway available. 4. Wing Flaps -- 40° (on final approach). 5. Airspeed -- 65 KIAS. 6. Doors -- UNLATCH PRIOR TO TOUCHDOWN. 7. Avionics Power and Master Switches -- OFF when landing is assured. 8. Touchdown -- SLIGHTLY TAIL LOW. 9. Mixture -- IDLE CUT-OFF. 10. Ignition Switch -- OFF. 11. Fuel Selector Valve -- OFF. 12. Airplane -- EVACUATE. LANDING WITHOUT POSITIVE INDICATION OF GEAR LOCKING 1. Before Landing Check -- COMPLETE. 2. Approach -- NORMAL (full flap). 3. Landing Gear and Gear Pump Circuit Breakers -- IN. 4. Landing -- TAIL LOW as smoothly as possible. 5. Braking -- MINIMUM necessary. 6. Taxi -- SLOWLY. 7. Engine -- SHUTDOWN before inspecting gear. LANDING WITH A DEFECTIVE NOSE GEAR (Or Flat Nose Tire) 1. Moveable Load -- TRANSFER to baggage area. 2. Passenger -- MOVE to rear seat. 3. Before Landing Checklist -- COMPLETE. 4. Runway -- HARD SURFACE or SMOOTH SOD. 5. Wing Flaps -- 40° 6. Cabin Doors -- UNLATCH PRIOR TO TOUCHDOWN. 7. Avionics Power and Master Switches -- OFF when landing is assured. 8. Land -- SLIGHTLY TAIL LOW. 9. Mixture -- IDLE CUT-OFF. 10. Ignition Switch -- OFF. 11. Fuel Selector Valve -- OFF. 12. Elevator Control-- HOLD NOSE OFF GROUND as long as possi- ble. 13. Airplane -- EVACUATE as soon as it stops. 1 October 1978 3-9 SECTION 3 EMERGENCY PROCEDURES CESSNA MODEL TR182 LANDING WITH A FLAT MAIN TIRE 1. Approach -- NORMAL (full flap). 2. Touchdown -- GOODTIRE FIRST, hold airplane off flat tire as long as possible with aileron control. 3. Directional Control -- MAINTAIN using brake on good wheel as required. ELECTRICAL POWER SUPPLY SYSTEM MALFUNCTIONS AMMETER SHOWS EXCESSIVE RATE OF CHARGE (Full Scale Deflection) 1. Alternator -- OFF. 2. Nonessential Electrical Equipment -- OFF. 3. Flight -- TERMINATE as soon as practical. lOW-VOLTAGE LIGHT ILLUMINATES DURING FLIGHT (Ammeter Indicates Discharge) NOTE Illumination of the low-voltage light may occur during low RPM conditions with an electrical load on the system such as during a low RPMtaxi. Under these conditions, the light will go out at higher RPM. The master switch need not be recycled since an over-voltage condition has not occurred to de-activate the alternator system. 1. Avionics Power Switch -- OFF. 2. Master Switch -- OFF (both sides). 3. Master Switch -- ON. 4. Low-Voltage Light -- CHECK OFF. 5. Avionics Power Switch -- ON. If low-voltage light illuminates again: 6. Alternator -- OFF. 7. Nonessential Radio and Electrical Equipment -- OFF. 8. Flight -- TERMINATE as soon as practical. 3-10 1 October 1978 CESSNA MODEL TR182 SECTION 3 EMERGENCY PROCEDURES AMPLIFIED PROCEDURES ENGINE FAILURE If an engine failure occurs during the takeoff run, the most important thing to do is stop the airplane on the remaining runway. Those extra items on the checklist will provide added safety after a failure of this type. Prompt lowering of the nose to maintain airspeed and establish a glide attitude is the first response to an engine failure after takeoff. In most cases, the landing should be planned straight ahead with only small changes in direction to avoid obstructions. Altitude and airspeed are seldom sufficient to execute a 1800 gliding turn necessary to return to the runway. The checklist procedures assume that adequate time exists to secure the fuel and ignition systems prior to touchdown. After an engine failure in flight, the best glide speed as shown in figure 3-1 should be established as quickly as possible. While gliding toward a suitable landing area, an effort should be made to identify the cause of the failure. If time permits, an engine restart should be attempted as shown in the checklist. If the engine cannot be restarted, a forced landing without power must be completed. * PROPELLER WINDMllliNG t:: 10,000 * flAPS & GEAR UP * ZERO WIND 3100 81 2600 74 2100 67 z ;i BODO I-------;.-----+--~~ a: UJ I- UJ > o en « l- I 19 UJ I BEST GLIDE SPEED WEIGHT (LBS) KIAS o 5 10 15 20 25 GROUND DISTANCE - NAUTICAL MILES Figure 3-1. Maximum Glide 1 October 1978 3-11 SECTION 3 EMERGENCY PROCEDURES CESSNA MODELTR182 FORCED LANDINGS If all attempts to restart the engine fail and a forced landing is imminent, select a suitable field and prepare for the landing as discussed in the checklist for Emergency Landing Without Engine Power. Before attempting an "off airport" landing with engine power availa- ble, one should fly over the landing area at a safe but low altitude to inspect the terrain for obstructions and surface conditions, proceeding as dis- cussed under the Precautionary Landing With Engine Power checklist. Prepare for ditching by securing or jettisoning heavy objects located in the baggage area and collect folded coats for protection of occupants' face at touchdown. Transmit Mayday message on 121.5 MHz giving location and intentions and squawk 7700 if a transponder is installed. Avoid a landing flare because of difficulty in judging height over a water surface. In a forced landing situation, do not turn off the avionics power and master switches until a landing is assured. Premature deactivation of the switches will di~a,blethe encoding altimeter and airplane electrical sys- tems. LANDING WITHOUT ELEVATOR CONTROL Trim for horizontal flight with an airspeed of approximately 80 KIAS by using throttle and elevator trim control. Then do not change the elevator trim control setting; control the glide angle by adjusting power exclu- sively. At flareout, the nose-down moment resulting from power reduction is an adverse factor and the airplane may hit on the nose wheel. Conse- quently, at flareout, the elevator trim control should be adjusted toward the full nose-up position and the power adjusted so that the airplane will rotate to the horizontal attitude for touchdown. Close the throttle at touchdown. FIRES Although engine fires are extremely rare in flight, the steps of the appropriate checklist should be followed if one is encountered. After completion of this procedure, execute a forced landing. Do not attempt to restart the engine. 3-12 1October 1978 CESSNA MODEL TR182 SECTION 3 EMERGENCY PROCEDURES The initial indication of an electrical fire is usually the odor ofburning insulation. The checklist for this problem should result in elimination of the fire. EMERGENCY OPERATION IN CLOUDS (Vacuum System Failure) In the event of a vacuum system failure during flight. the directional indicator and attitude indicator will be disabled, and the pilot will have to rely on the turn coordinator if he inadvertently flies into clouds. The following instructions assume that only the electrically-powered turn coordinator is operative, and that the pilot is not completely proficient in instrument flying. EXECUTING A 1800 TURN IN CLOUDS Upon inadvertently entering the clouds, an immediate plan should be made to turn back as follows: 1. Note the compass heading. 2. Note the time of the minute hand and observe the position of the sweep second hand on the clock. 3. When the sweep second hand indicates the nearest half-minute, initiate a standard rate left turn, holding the turn coordinator symbolic airplane wing opposite the lower left index mark for 60 seconds. Then roll back to level flight by leveling the miniature airplane. 4. Check accuracy of the turn by observing the compass heading 'which should be the reciprocal of the original heading. 5. If necessary, adjust heading primarily with skidding motions rather than rolling motions so that the compass will read more accurately. 6. Maintain altitude and airspeed by cautious application of elevator control. Avoid overcontrolling by keeping the hands offthe control wheel B,S much as possible and steering only with rudder. EMERGEr..lCY DESCENT THROUGH CLOUDS If conditions preclude reestablishment of VFR flight by a 1800 turn, a descent through a cloud deck to VFR conditions may be appropriate. If possible, obtai.nradio clearance for an ern.ergencydescent through clouds. To guard against a spiral dive, choose an easterly or westerly heading to minimize compass card swings due to changing bank angles. In addition, keep hands off the control wheel and steer a straight course with rudder control by monitoring the turn coordinator. Occasionally check the 1 October 1978 3-13 SECTION 3 EMERGENCYPROCEDURES CESSNA MODELTR182 compass heading and make minor corrections to hold an approximate course. Before descending into the clouds, set up a stabilized let-down condition as follows: 1. Extend landing gear. 2. Apply full rich mixture. 3. Apply full carburetor heat. 4. Reduce power to set up a 500to 800 ft/min rate of descent. 5. Adjust the elevator and rudder trim control wheels for a stabilized descent at 80 KIAS. 6. Keep hands off control wheel. 7. Monitor turn coordinator and make corrections by rudder alone. 8. Adjust rudder trim to relieve unbalanced rudder force, if present. 9. Check trend of compass card movement and make cautious corrections with rudder to stop turn. 10. Upon breaking out of clouds, resume normal cruising flight. RECOVERY FROM A SPIRAL DIVE If a spiral is encountered, proceed as follows: 1. Close the throttle. 2. Stop the turn by using coordinated aileron and rudder control to align the symbolic airplane in the turn coordinator with the horizon reference line. 3. Cautiously apply elevator back pressure to slowly reduce the indicated airspeed to 80 KIAS. 4. Adjust the elevator trim control to maintain an 80 KIAS glide. 5. Keep hands off the control wheel, using rudder control to hold a straight heading. Use rudder trim to relieve unbalanced rudder force, if present. o. Apply carburetor heat as necessary. 7. Clear engine occasionally, but avoid using enough power to disturb the trimmed glide. 8. Upon breaking out of clouds, resume normal cruising flight. INADVERTENT FLIGHT INTO ICING CONDITIONS Flight into icing conditions is prohibited. An inadvertent encounter with these conditions can best be handled using the checklist procedures. The best procedure, of course, is to turn back or change altitude to escape icing conditions. 3-14 1 October 1978 CESSNA MODEL TR182 SECTION 3 EMERGENCY PROCEDURES STATIC SOURCE BLOCKED If erroneous readings of the static source instruments (airspeed, altimeter and rate-of-climb) are suspected, the alternate static source valve should be pulled on, thereby supplying static pressure to these instruments from the cabin, Cabin pressures will vary with open ventila- tors or windows and with airspeed, To avoid the possibility of large errors, the windows should not be open when using the alternate static source. NOTE In an emergency on airplanes not equipped with an alternate static source, cabin pressure can be supplied to the static pressure instruments by breaking the glass in the face of the rate-of-climb indicator. A calibration table is provided in Section 5 to illustrate the effect of the alternate static source on indicated airspeeds. With the windows and vents closed the airspeed indicator may typically read as much as 4 knots faster and the altimeter 40 feet higher in cruise. With the vents open, the speed variation reduces to 1 knot or less. If the alternate static source must be used for landing, the normal indicated approach speed may be used since the indicated airspeed variations in this configuration are 3 knots or less. SPINS Intentional spins IU8 prohibited in this airplane. Should an inadvert- ent spin occur, the following recovery procedure should be used: 1. RETARD THROTTLE TO IDLE POSITION. 2. PLACE AILERONS IN NEUTRAL POSITION. 3. APPLY AND HOLD FULL RUDDER OPPOSITE TO THE DIREC- TION OF ROTATION. 4. JUST AFTER THE RUDDER REACHES THE STOP, MOVETHE WHEEL BRISKLY FORWARD FAR ENOUGH TO BREAK THE STALL. Full down elevator may be required at aft center of gravity loadings to assure optimum recoveries. 5. HOLD THESE CONTROL INPUTS UNTIL ROTATION STOPS Premature relaxation of the control inputs may extend the recov- ery. 6. AS ROTATION STOPS, NEUTRALIZE RUDDER, AND MAKE A SMOOTHRECOVERY FROM THE RESULTING DIVE. NOTE If disorientation precludes a visual determination of the direction of rotation, the symbolic airplane in the turn coordinator may be referred to for this information. 1 October 1978 3-15 SECTION 3 EMERGENCY PROCEDURES CESSNA MODEL TR182 ROUGH ENGINE OPERATION OR LOSS OF POWER CARBURETOR ICING An unexplained drop in manifold pressure and eventual engine roughness may result from the formation of carburetor ice. To clear the ice, apply full throttle and pull the carburetor heat knob full out until the engine runs smoothly; then remove carburetor heat and readjust the throttle. If conditions require the continued use of carburetor heat in cruise flight, use the minimum amount of heat necessary to prevent ice from forming and lean the mixture for smoothest engine operation. At high altitudes, manifold pressure drop with the application of carburetor heat may be as much as 10 inches Hg. In this case, advance the throttle as necessary to obtain the desired power or full throttle, whichever is less. SPARK PLUG FOULING A slight engine roughness in flight may be caused by one or more spark plugs becoming fouled by carbon or lead deposits. This may be verified by turning the ignition switch momentarily from BOTHto either L or R position. An obvious power loss in single ignition operation is evidence of spark plug or magneto trouble. Assuming that spark plugs are the more likely cause, lean the mixture to the recommended lean setting for cruising flight. If the problem does not clear up in several minutes, determine if a richer mixture setting will produce smoother operation. If not, proceed to the nearest airport for repairs using the BOTH position of the ignition switch unless extreme roughness dictates the use of a single ignition position. MAGNETO MALFUNCTION A sudden engine roughness or misfiring is usually evidence of magneto problems. Switching from BOTHto either L or R ignition switch position will identify which magneto is malfunctioning. Select different power settings and enrichen the mixture to determine if continued opera- tion on BOTH magnetos is practicable. If not, switch to the good magneto and proceed to the nearest airport for repairs. ENGINE - DRIVEN FUEL PUMP FAILURE In the event of an engine-driven fuel pump failure, gravity flow will provide sufficient fuel flow for level or descending flight. However, in a climbing attitude or anytime the fuel pressure drops to 0.5 PSI, the auxiliary fuel pump should be turned on. 3-16 1 October 1978 CESSNA MODEL TR182 SECTION 3 EMERGENCY PROCEDURES LOW OIL PRESSURE If low oil pressure is accompanied by normal oil temperature, there is a possibility the oil pressure gage or relief valve is malfunctioning. A leak in the line to the gage is not necessarily cause for an immediate precau- tionary landing because an orifice in this line will prevent a sudden loss of oil from the engine sump. However, a landing at the nearest airport would be advisable to inspect the source of trouble. If a total loss of oil pressure is accompanied by a rise in oil tempera- ture, there is good reason to suspect an engine failure is imminent. Reduce engine power immediately and select a suitable forced landing field. Use only the minimum power required to reach the desired touchdown spot. LANDING GEAR MALFUNCTION PROCEDURES In the event of possible landing gear retraction or extension malfunc- tions, there are several general checks that should be made prior to initiating the steps outlined in the following paragraphs. In analyzing a landing gear malfunction, first check that the master switch is ON and the LDG GEAR and GEAR PUMP circuit breakers are in; reset, if necessary. Also, check both landing gear position indicator lights for operation by "pressing-to-test" the light units and rotating them at the same time to check for open dimming shutters. A burned-out bulb can be replaced in flight by using the bulb from the remaining gear position indicator light. RETRACTION MALFUNCTIONS If the landing gear fails to retract normally, or an intermittent GEAR UP indicator light is present, check the indicator light for proper operation and attempt to recycle the landing gear. Place the landing gear lever in the GEAR DOWNposition. When the GEAR DOWNlight illuminates, reposi- tion the gear lever in the GEAR UP position for another retraction attempt. If the GEAR UP indicator light still fails to illuminate, the flight may be continued to an airport having maintenance facilities, if practical. If gear motor operation is audible after a period of one minute following gear lever retraction actuation, pull the GEAR PUMP circuit breaker switch to prevent the electric motor from overheating. In this event, remember to re- engage the circuit breaker switch just prior to landing. Intermittent gear motor operation may also be detected by momentary fluctuations of the ammeter needle. 1 October 1978 3-17 SECTION 3 EMERGENCY PROCEDURES CESSNA MODELTR182 EXTENSION MALFUNCTIONS Normallanding gear extension time is approximately 5 seconds. If the landing gear will not extend normally, perform the general checks of circuit breakers and master switch and repeat the normal extension procedures at a reduced airspeed of 100KIAS. The landing gear lever must be in the down position with the detent engaged. If efforts to extend and lock the gear through the normal landing gear system fail, the gear can be manually extended (as long as hydraulic system fluid has not been cmnpletely lost) by use of the emergency hand pump. The hand pump is located between the front seats. A checklist is provided for step-by-step instructions for a manual gear extension. If gear motor operation is audible after a period of one minute following gear lever extension actuation, pull the GEAR PUMP circuit breaker to prevent the electric motor from overheating. In this event, remember to re-engage the circuit breaker just prior to landing. GEAR UP LANDINGS If the landing gear remains retracted or is only partially extended, and all efforts to fully extend it (including manual extension) have failed, plan a wheels-up landing. In preparation for landing, reposition the landing gear lever to GEAR UP and push the LDG GEAR and GEAR PUMP circuit breakers in to allow the landing gear to swing into the gear wells at touchdown. Then proceed in accordance with the checklist. ELECTRICAL POWER SUPPLY SYSTEM MALFUNCTIONS Malfunctions in the electrical power supply system can be detected by periodic monitoring of the ammeter and low-voltage warning light; however, the cause of these malfunctions is usually difficult to determine. A broken alternator drive belt or wiring is most likely the cause of alternator failures, although other factors could cause the problem. A damaged or improperly adjusted alternator control unit can also cause malfunctions. Problems of this nature constitute an electrical emergency and should be dealt with immediately. Electrical power malfunctions usually fall into two categories: excessive rate of charge and insufficient rate of charge. The paragraphs below describe the recommended remedy for each situation. 3-18 1 October 1978 CESSNA MODELTR182 SECTION 3 EMERGENCY PROCEDURES EXCESSIVE RATE OF CHARGE After engine starting and heavy electrical usage at low engine speeds (such as extended taxiing) the battery condition will be low enough to accept above normal charging during flight, the ammeter should be indicating less than two needle widths of charging current. If the charging rate were to remain above this value on a long flight, the battery would overheat and evaporate the electrolyte at an excessive rate. Electronic components in the electrical system can be adversely affected by higher than normal voltage. The alternator control unit includes an over-voltage sensor which normally will automatically shut down the alternator if the charge voltage reaches approximately 31.5volts. If the over-voltage sensor malfunctions or is improperly adjusted, as evidenced by an excessive rate of charge shown on the ammeter, the alternator should be turned off, nonessential electrical equipment turned off and the flight terminated as soon as practical. INSUFFICIENT RATE OF CHARGE NOTE Illumination of the low-voltage light and ammeter dis- charge indications may occur during low RPM conditions with an electrical load on the system, such as during a low RPM taxi. Under these conditions, the light will go out at higher RPM. The master switch need not be recycled since an over-voltage condition has not occurred to de-activate the alternator system. If the over-voltage sensor should shut down the alternator, a discharge rate will be shown On the ammeter followed by illumination of the low- voltage warning light. Since this may be a "nuisance" trip-out, an attempt should be made to reactivate the alternator system. To do this, turn the avionics power switch off, then turn both sides of the master switch off and then on again. If the problem no longer exists, normal alternator charging will resume and the low-voltage light will go off. The avionics power switch may then be turned back on. If the light illuminates again, a malfunction is confirmed. In this event, the flight should be terminated and/ or the current drain on the battery minimized because the battery can supply the electrical system for only a limited period of time. If the emergency occurs at night, power must be conserved for later operation of the landing gear and wing flaps and possible use of the landing lights during landing. 1 October 1978 3-19/(3-20blank) CESSNA MODEL TR182 SECTION 4 NORMAL PROCEDURES SECTION 4 NORMAL PROCEDURES TABLE OF CONTENTS Page Introduction . . . . . . . . . Speeds For Normal Operation 4-3 . 4-3 CHECKLIST PROCEDURES Preflight Inspection Cabin ..... Empennage Right Wing, Trailing Edge Right Wing Nose . Left Wing . Left Wing, Leading Edge Left Wing, Trailing Edge Before Starting Engine Starting Engine Before Takeoff . . . Takeoff . Normal Takeoff Short Field Takeoff Enroute Climb . . . . Normal Climb . . Maximum Performance Climb Cruise Descent .... Before Landing Landing .... Normal Landing Short Field Landing Balked Landing After Landing . . Securing Airplane 4-5 4-5 4-5 4-5 4-5 4-6 4-6 4-6 4-7 4-7 4-7 4-8 4-9 4-9 4-9 4-10 4-10 4-10 4-10 4·10 4-10 4-11 4-11 4-11 4-11 4-12 4-12 1 October 1978 4-1 SECTION 4 NORMAL PROCEDURES TABLE OF CONTENTS (Continued) AMPLIFIED PROCEDURES Starting Engine Taxiing .... Before Takeoff . Warm-Up Magneto Check Alternator Check Takeoff . Power Check . . Wing Flap Settings Crosswind Takeoff Landing Gear Retraction Enroute Climb Cruise Stalls .... Before Landing Landing .... Normal Landing Short Field Landing Crosswind Landing . Balked Landing Cold Weather Operation Starting ..... Operation Hot Weather Operation Noise Abatement 4-2 CESSNA MODELTR182 Page 4-13 4-13 4-15 4-15 4-15 4-15 4-15 4-15 4-16 4-16 4-16 4-17 4-17 4-19 4-20 4-20 4-20 4-20 4-20 4-21 4-21 4-21 4-22 4-23 4-23 1 October 1978 CESSNA MODEL TR182 SECTION 4 NORMAL PROCEDURES INTRODUCTION Section 4 provides checklist and amplified procedures for the conduct of normal operation. Normal procedures associated with optional systems can be found in Section 9. SPEEDS FOR NORMAL OPERATION Unless otherwise noted, the following speeds are based on a maximum weight of 3100pounds and may be used for any lesser weight. However, to achieve the performance specified in Section 5 for takeoff distance, the speed appropriate to the particular weight must be used. Takeoff: Normal Climb Out . Short Field Takeoff, Flaps 20°, Speed at 50 Feet Enroute Climb, Flaps and Gear Up: Normal . Best Rate of Climb. Sea Level . Best Rate of Climb, 20,000Feet Best Angle of Climb, Sea Level Best Angle of Climb, 10,000Feet Landing Approach: Normal Approach, Flaps Up Normal Approach, Flaps 40° Short Field Approach, Flaps 40° Balked Landing: Maximum Power, Flaps 20° .. Maximum Recommended Turbulent Air Penetration Speed: 3100 Lbs 2600 Lbs . 2100 Lbs . Maximum Demonstrated Crosswind Velocity: Takeoff or Landing . . . . . . . . . . . 70-80 KIAS 59 KIAS .90-100 KIAS 88 KIAS" 85 KIAS 72 KIAS 74 KIAS 70-80KIAS 65-75 KIAS 64 KIAS 70 KIAS 112 KIAS 102 KIAS 91 KIAS 18 KNOTS 1 October 1978 4-3 SECTION 4 NORMAL PROCEDURES CESSNA MODEL TR182 NOTE Visually check airplane for general condition during walk-around inspection. In cold weather, remove even small accumulations of frost, ice or snow from wing, tail and control surfaces. Also, make sure that control surfaces contain no internal accumulations of ice or debris. Prior to flight, check that pitot heater (if installed) is warm to touch within 30 seconds with battery and pitot heat switches on. If a night flight is planned, check operation of all lights, and make sure a flashlight is available. Figure 4-1. Preflight Inspection 4-4 1 October 1978 CESSNA MODEL TR182 SECTION 4 NORMAL PROCEDURES CHECKLIST PROCEDURES PREFLIGHT INSPECTION (DCABIN 1. Pilot's Operating Handbook -- AVAILABLE IN THE AIRPLANE. 2. Landing Gear Lever -- DOWN. 3. Control Wheel Lock -- REMOVE. 4. Ignition Switch -- OFF. 5. Avionics Power Switch -- OFF. 6. Master Switch -- ON. I WARNING I When turning on the master switch, using an external power source, or pulling the propeller through by hand, treat the propeller as if the ignition switch were on. Do not stand, nor allow anyone else to stand, within the arc of the propeller, since a loose or broken wire, or a component malfunction, could cause the propeller to rotate. 7. Fuel Quantity Indicators -- CHECK QUANTITY. 8. Landing Gear Position Indicator Light (green) -- ILLUMINATED. 9. Master Switch -- OFF. 10. Static Pressure Alternate Source Valve -- OFF. 11. Fuel Selector Valve -- BOTH. 12. Baggage Door -- CHECK for security, lock with key if child's seat is to be occupied. ®EMPENNAGE 1. Rudder Gust Lock -- REMOVE. 2. Tail Tie-Down -- DISCONNECT. 3. Control Surfaces -- CHECK freedom of movement and security. @RIGHT WING Trailing Edge 1. Aileron -- CHECK freedom of movement and security. 0RIGHTWING 1. Wing Tie-Down -- DISCONNECT. 2. Fuel Tank Vent Opening -- CHECK for stoppage. 1 October 1978 4-5 SECTION 4 NORMAL PROCEDURES CESSNA MODEL TR182 3. Main Wheel Tire -- CHECK for proper inflation. 4. Before first flight of the day and after each refueling, use sampler cup and drain small quantity of fuel from fuel tank sump quick- drain valve to check for water, sediment, and proper fuel grade. 5. Fuel Quantity -- CHECK VISUALLY for desired level. 6. Fuel Filler Cap -- SECURE and vent unobstructed. ®NOSE 1. Static Source Openings (both sides of fuselage) --CHECK for stoppage. 2. Propeller and Spinner -- CHECK for nicks, security and oil leaks. 3. Landing Lights -- CHECK for condition and cleanliness. 4. Engine Induction Air Inlet -- CHECK for restrictions. 5. Nose Wheel Strut and Tire -- CHECK for proper inflation. 6. Nose Tie-Down -- DISCONNECT. 7. Engine Oil Level -- CHECK. Do not operate with less than five quarts. Fill to eight quarts for extended flight. NOTE To check oil level, remove dipstick, wipe clean and re- insert. Wait 5 seconds and then check oil level for an accurate reading. 8. Before first flight of the day and after each refueling, pull out strainer drain knob for about four seconds to clear fuel strainer of possible water and sediment. Check strainer drain closed. If water is observed, the fuel system may contain additional water, and further draining of the system at the strainer, fuel tank sumps, and fuel selector valve drain plug will be necessary. ® LEFT WING 1. Main Wheel Tire -- CHECK for proper inflation. 2. Before first flight of day and after each refueling, use sampler cup and drain small quantity of fuel from fuel tank sump quick-drain valve to check for water, sediment and proper fuel grade. 3. Fuel Quantity -- CHECK VISUALLY for desired level. 4. Fuel Filler Cap -- SECURE and vent unobstructed. (f)LEFT WING Leading Edge 1. Pitot Tube Cover -- REMOVE and check opening for stoppage. 2. Fuel Tank Vent Opening -- CHECK for stoppage. 3. Stall Warning Vane -- CHECK for freedom of movement while master switcn is momentarily turned ON (horn should sound when 4-6 1 October 1978 CESSNA MODEL TR182 SECTION 4 NORMAL PROCEDURES vane is pushed upward). 4. Wing Tie-Down -- DISCONNECT. ®LEFT WING Trailing Edge 1. Aileron -- CHECK freedom of movement and security. BEFORE STARTING ENGINE 1. Preflight Inspection -- COMPLETE. 2. Seats, Belts, Shoulder Harnesses -- ADJUST and LOCK. 3. Fuel Selector Valve -- BOTH. 4. Avionics Power Switch, Autopilot (if installed), Electrical Equip- ment -- OFF. CAUTION The avionics power switch must be OFF during engine start to prevent possible damage to avionics. 5. Brakes -- TEST and SET. 6. Cowl Flaps -- OPEN (move lever out of locking hole to reposition). 7. Landing Gellr Lever -- DOWN 8. Circuit Breakers -- CHECK IN. STARTING ENGINE 1. Mixture -- RICH. 2. Propeller -- HIGH RPM. 3. Carburetor Heat -- COLD. 4. Throttle -- CLOSED. NOTE The carburetor does not have an accelerator pump; there- fore, pumping of the throttle must be avoided during starting because doing so will only cause excessive lean- ing. 5. Prime -- AS REQUIRED (2 to 4 strokes in cold weather). 6. Master Switch -- ON. 7. Auxiliary Fuel Pump -- ON (check for rise in fuel pressure), then OFF. 1 October 1978 4-7 SECTION 4 NORMAL PROCEDURES CESSNA MODEL TR182 8. Propeller Area -- CLEAR. 9. Ignition Switch -- START (release when engine starts). NOTE If engine does not start after 5 seconds of cranking in warm weather, crack throttle 1/8 inch and crank again. 10. Oil Pressure -- CHECK. 11. Low-Voltage Light -- OFF (at approximately 1000RPM). BEFORE TAKEOFF 1. Cabin Doors and Windows -- CLOSED and LOCKED. 2. Parking Brake -- SET. 3. Flight Controls -- FREE and CORRECT. 4. Flight Instruments -- SET. 5. Fuel Selector Valve -- BOTH. 6. Mixture -- RICH. NOTE In flight, gravity feed will normally supply satisfactory fuel flow if the engine-driven fuel pump should fail. However, if a fuel pump failure causes the fuel pressure to drop below 0.5 PSI, use the auxiliary fuel pump to assure proper engine operation. 8. Elevator and Rudder Trim -- TAKEOFF. 9. Throttle -- i700 RPM. a. Magnetos -- CHECK (RPM drop should not exceed 175RPM on either magneto or 50 RPM differential between magnetos). b. Propeller -- CYCLEfrom high to low RPM; return to high RPM (full in). c. Carburetor Heat -- CHECK (for RPM drop and indication on carburetor temperature gage). d. Engine Instruments and Ammeter -- CHECK. e. Suction Gage -- CHECK. 10. Avionics Power Switch -- ON. li. Radios -- SET. 12. Autopilot (if installed) -- OFF. 13. Flashing Beacon, Navigation Lights and/ or Strobe Lights -- ON as required. 14. Throttle Friction Lock -- ADJUST. 15. Parking Brake -- RELEASE. 4-8 1 October 1978 CESSNA MODEL TR182 SECTION 4 NORMAL PROCEDURES TAKEOFF NORMAL TAKEOFF L Wing Flaps -- 0° - 20°. 2. Carburetor Heat -- COLD. 3. Power -- 31 INCHES Hg (Maximum) and 2400RPM. NOTE To avoid overboosting the engine, do not use full throttle for takeoff. 4. Mixture -- FULL RICH. 5. Elevator Control -- LIFT NOSE WHEEL AT 55 KIAS. NOTE When the nose wheel is lifted, the gear motor may run 1-2 seconds to restore hydraulic pressure. 6. Climb Speed -- 70 KIAS (flaps 20°). 80 KIAS (flaps UP). 7. Brakes -- APPLY momentarily when airborne. 8. Landing Gear -- RETRACT in climb out. 9. Wing Flaps -- RETRACT. SHORT FIELD TAKEOFF 1. Wing Flaps -- 20°. 2. Carburetor Heat -- COLD. 3. Brakes -- APPLY. 4. Power -- 31 INCHES Hg (Maximum) and 2400 RPM. NOTE To avoid overboosting the engine, do not use full throttle for takeoff. 5. Mixture -- FULL RICH. 6. Brakes -- RELEASE. 7. Elevator Control -- MAINTAIN SLIGHTLY TAIL-LOW ATTI- TUDE. - 8. Climb Speed -- 59 KIAS until all obstacles are cleared. 9. Landing Gear -- RETRACT after obstacles are cleared. "'10. Wing Flaps -- RETRACT slowly after reaching 75 KIAS. 1 October 1978 4-9 SECTION 4 NORMAL PROCEDURES CESSNA MODEL TR182 ENROUTE CLIMB NORMAL CLIMB 1. Airspeed -- 90-100 KIAS. 2. Power -- 25 INCHES Hg and 2400 RPM. 3. Fuel Selector Valve -- BOTH. 4. Mixture -- FULL RICH. 5. Cowl Flaps -- OPEN as required. MAXIMUM PERFORMANCE CLIMB 1. Airspeed -- 88 KIAS at sea level to 85 KIAS at 20,000 feet. 2. Power -- 31 INCHES Hg and 2400 RPM. 3. Fuel Selector Valve -- BOTH. 4. Mixture -- FULL RICH. 5. Cowl Flaps -- FULL OPEN. CRUISE 1. Power -- 17-25 INCHES Hg, 2100-2400RPM. 2. Elevator and Rudder Trim -- ADJUST. 3. Mixture -- LEAN. 4. Cowl Flaps -- CLOSED. DESCENT 1. Fuel Selector Valve -- BOTH. 2. Power -- AS DESIRED. 3. Carburetor Heat -- AS REQUIRED to prevent carburetor icing. 4. Mixture -- LEAN for smoothness. 5. Cowl Flaps -- CLOSED. 6. Wing Flaps -- AS DESIRED (0° -10° below 140KIAS, 10°- 40°below 95 KIAS). NOTE The landing gear may be used below 140KIAS to increase the rate of descent. BEFORE LANDING 1. Seats, Belts, Shoulder Harnesses -- ADJUST and LOCK. 2. Fuel Selector Valve -- BOTH. 4-10 1 October 1978 CESSNA MODEL TR182 SECTION 4 NORMAL PROCEDURES 3. Landing Gear -- DOWN (below 140 KIAS). 4. Landing Gear -- CHECK (observe main gear down and green indicator light illuminated). 5. Mixture -- RICH. 6. Carburetor Heat -- ON (apply full heat before closing throttle). 7. Propeller -- HIGH RPM. 8. Autopilot (if installed) -- OFF. LANDING NORMAL LANDING 1. Airspeed -- 70-80 KIAS (flaps UP). 2. Wing Flaps -- AS DESIRED (0°_10° below 140KIAS, 10°_40°below 95 KIAS). 3. Airspeed -- B5-'75RIA9 (fl~ps DOWN). 4. Trim -- ADJUST. 5. Touchdown -- MAIN WHEELS FIRST. 6. Landing Roll -- LOWER NOSE WHEEL GENTLY. 7. Braking -- MINIMUM REQUIRED. SHORT FIELD LANDING 1. Airspeed -- 70-80 KIAS (flaps UP). 2. Wing Flaps -- 40° (below 95 KIAS). 3. Airspeed -- MAINTAIN 64 KIAS. 4. Trim -- ADJUST. 5. Power -- REDUCE to idle as obstacle is cleared. 6. Touchdown -- MAIN WHEELS FIRST. 7. Brakes -- APPLY HEAVILY. 8. Wing Flaps -- RETRACT for maximum brake effectiveness. BALKED LANDING 1. Power -- 31 INCHES Hg and 2400 RPM. 2. Wing Flaps -- RETRACT to 20°. 3. Climb Speed -- 70 KIAS until all obstacles are cleared. 4. Wing Flaps -- RETRACT slowly after reaching 75 KIAS. 5. Cowl Flaps -- OPEN. 6. Manifold Pressure -- REDUCE TO 25 INCHES Hg. 7. Carburetor Heat -- COLD. 8. Power -- READJUST as desired. 1 October 1978 4-11 SECTION 4 NORMAL PROCEDURES CESSNA MODEL TR182 AFTER lANDING 1. Wing Flaps -- UP. 2. Carburetor Heat -- COLD. 3. Cowl Flaps -- OPEN. SECURING AIRPLANE 1. Parking Brake -- SET. 2. Throttle -- IDLE. 3. Avionics Power Switch, Electrical Equipment -- OFF. 4. Mixture -- IDLE CUT-OFF (pulled full out). 5. Ignition Switch -- OFF. 6. Master Switch -- OFF. 7. Control Lock -- INSTALL. 8. Fuel Selector Valve -- RIGHT or LEFT to prevent crossfeeding. 4-12 1 October 1978 CESSNA MODEL TR182 SECTION 4 NORMAL PROCEDURES AMPLIFIED PROCEDURES STARTING ENGINE Proper fuel management and throttle adjustments are the determining factors in securing an easy start from your turbocharged, carbureted engine. The procedure outlined in this section should be followed closely as it is effective under nearly all operating conditions. Conventional full rich mixture and high RPM propeller settings are used for starting; however, the throttle should be fully closed. When ready to start, place the ignition switch in the start position. In warm weather, if the engine does not start after 5 seconds of cranking, crack the throttle 1/8 inch open and crank again. When the engine starts, slowly adjust the throttle to the desired idle speed. NOTE The carburetor used on this airplane does not have an accelerator pump; therefore, pumping of the throttle must be avoided during starting because doing so will only cause excessive leaning. In cold weather, 2 strokes of the primer may be necessary prior to starting. During extremely cold temperatures, up to 4 strokes of the primer may be necessary. NOTE Additional details concerning cold weather starting and operation may be found under COLDWEATHER OPERA- TIoN paragraphs in this section. TAXIING When taxiing, it is important that speed and use of brakes be held to a minimum and that all controls be utilized (see Taxiing Diagram, figure 4- 2) to maintain directional control and balance. The carburetor heat control knob should be pushed full in during all ground operations unless heat is absolutely necessary for smooth engine operation. When the knob is pulled out to the heat position, air entering the engine is not filtered. 1 October 1978 4-13 SECTION 4 NORMAL PROCEDURES CESSNA MODEL TR182 ., CODE NOTE WIND DIRECTION • Strong quartering tail winds require caution. Avoid sudden bursts of the throttle and sharp braking when the airplane is in this attitude. Use the steerable nose wheel and rudder to maintain direction. Figure 4-2. Taxiing Diagram 4-14 1 October 1978 CESSNA MODELTR182 SECTION 4 NORMALPROCEDURES Taxiing over loose gravel or cinders should be done at low engine speed to avoid abrasion and stone damage to the propeller tips. BEFORE TAKEOFF WARM-UP Since the engine is closely cowled for efficient in-flight cooling, precautions should be taken to avoid overheating on the ground. Full power checks on the ground are not recommended unless the pilot has good reason to suspect that the engine is not turning up properly. MAGNETO CHECK The magneto check should be made at 1700RPM as follows. Move ignition switch first to R position and note RPM.Next move switch back to BOTHto clear the other set of plugs. Then move switch to the L position, note RPMand return the switch to the BOTHposition. RPMdrop should not exceed 175RPM on either magneto or show greater than 50RPM differen- tial between magnetos. If there is a doubt concerning operation of the ignition system, RPM checks at higher engine speeds will usually confirm whether a deficiency exists. An absence of RPM drop may be an indication of faulty grounding of one side of the ignition system or should be cause for suspicion that the magneto timing is set in advance of the setting specified. ALTERNATOR CHECK Prior to flights where verification of proper alternator and alternator control unit operation is essential (such as night or instrument flights), a positive verification can be made by loading the electrical system momentarily (3 to 5 seconds) with the landing lights during the engine runup (1700RPM). The ammeter will remain within a needle width of the initial reading if the alternator and alternator control unit are operating properly. TAKEOFF POWER CHECK It is important to check takeoff power early in the takeoff run. Full throttle will not be necessary to maintain the maximum rated manifold pressure. Any sign of rough engine operation or sluggish engine accelera- tion is good cause for discontinuing the takeoff. 1 October 1978 4-15 SECTION 4 NORMAL PROCEDURES CESSNA MODEL TR182 Full power runups over loose gravel are especially harmful to pro- peller tips. When takeoffs must be made over a gravel surface, it is very important that the throttle be advanced slowly. This allows the airplane to start rolling before high RPM is developed, and the gravel will be blown back of the propeller rather than pulled into it. When unavoidable small dents appear in the propeller blades they should be corrected immediately as described in Section 8 under Propeller Care. After a manifold pressure of 31 inches Hg is obtained, adjust the throttle friction lock clockwise to prevent the throttle from creeping from a maximum power position. Similar friction lock adjustment should be made as required in other flight conditions to maintain a fixed throttle setting. WING FLAP SETTINGS Normal takeoffs are accomplished with wing flaps 0° to 20°. Using 20° wing flaps reduces the ground run and total distance over an obstacle by approximately 20 per cent. Flap deflections greater than 20° are not approved for takeoff. If 20° wing flaps are used for takeoff, they should be left down until all obstacles are cleared and a safe flap retraction speed of 70 KIAS is reached. To clear an obstacle with wing flaps 20°, an obstacle clearance speed of 59 KIAS should be used. Soft field takeoffs are performed with 20° flaps by lifting the airplane off the ground as soon as practical in a slightly tail-low attitude. If no obstacles are ahead, the airplane should be leveled off immediately to accelerate to a safer climb speed. With wing flaps retracted and no obstructions ahead, a climb-out speed of 80 KIAS would be most efficient. CROSSWIND TAKEOFF Takeoffs into strong crosswinds normally are performed with the minimum flap setting necessary for the field length, to minimize the drift angle immediately after takeoff. With the ailerons partially deflected into the wind, the airplane is accelerated to a speed slightly higher than normal, and then pulled off abruptly to prevent possible settling back to the runway while drifting. When clear of the ground, make a coordinated turn into the wind to correct for drift. LANDING GEAR RETRACTION Landing gear retraction normally is started after reaching the point 4-16 1 October 1978 CESSNA MODEL TR182 SECTION 4 NORMAL PROCEDURES over the runway where a wheels-down, forced landing on that runway would become impractical. Since the landing gear swings downward approximately two feet as it starts the retraction cycle, damage can result by retracting it before obtaining at least that much ground clearance. Before retracting the landing gear, the brakes should be applied momentarily to stop wheel rotation. Centrifugal force caused by the rapidly-spinning wheel expands the diameter of the tire. If there is an accumulation of mud or ice in the wheel wells, the rotating wheel may rub as it is retracted into the wheel well. ENROUTE CLIMB Normal climbs are performed at 90-100KIAS with flaps up, 25 inches of manifold pressure, 2400RPM, and full rich mixture for the best combina- tion of engine cooling, rate of climb and forward visibility. If it is necessary to climb rapidly to clear mountains or reach favorable winds at high altitudes, the best rate-of-climb speed should be used with maximum power of 31 inches Hg, 2400RPM and full rich mixture. This speed is 88 KIAS at sea level, decreasing to 85 KIAS at 20,000feet. If an obstruction ahead requires a steep climb angle, a best angle-of- climb speed should be used with landing gear and flaps up and maximum power. This speed is 72 KIAS at sea level, increasing to 74 KIAS at 10,000 feet. CRUISE Normal cr-uram g is performed between 55% and 75% power. The corresponding power settings and fuel consumption for various altitudes can be determined by using your Cessna Power Computer or the data in Section 5. NOTE Cruising should be done at 25 inches Hg and 2400RPM as much as practical until a total of 50 hours has accumulated or oil consumption has stabilized. This is to ensure proper seating of the rings and is applicable to new engines, and engines in service following cylinder replacement or top overhaul of one or more cylinders. 1 October 1978 4-17 SECTION 4 NORMAL PROCEDURES CESSNA MODELTR182 75% POWER 65% POWER 55% POWER ALTITUDE KTAS NMPG KTAS NMPG KTAS NMPG 5000 151 10.6 142 11.5 132 12.5 10,000 158 11.1 148 12.0 137 12.9 15,000 165 11.6 155 12.5 142 13.4 20,000 173 12.1 162 13.1 147 13.9 Standard Conditions Zero Wind Figure 4-3. Cruise Performance Table The Cruise Performance Table, figure 4-3,illustrates the true airspeed and nautical miles per gallon during cruise for various altitudes and percent powers. This table should be used as a guide, along with the available winds aloft information, to determine the most favorable alti- tudes and power setting for a given trip. The selection of cruise altitude on the basis of the most favorable wind conditions and the use of low power settings are significant factors that should be considered on every trip to reduce fuel consumption. For reduced noise levels, it is desirable to select the lowest RPM in the green arc range for a given percent power that will provide smooth engine operation. The cowl flaps should be opened, if necessary, to maintain the cylinder head temperature at approximately two-thirds of the normal operating range (green arc). Cruise performance data in this handbook and on the power computer is based on a recommended lean mixture setting which is established by reference to exhaust gas temperature (EGT) as shown on the Cessna Economy Mixture Indicator. EGT is used for mixture leaning in cruising flight at maximum recommended cruise power or less. To adjust the mixture, lean to establish the peak EGT as a reference point and then enrichen the mixture by a desired increment based on data in figure 4-4. The mixture should be full rich at any power setting above maximum recommended cruise power. As noted in the table, operation at peak EGT provides best fuel economy. This results in approximately 7% greater range than shown in this handbook accompanied by approximately 4 knots decrease in speed. When leaning the mixture under some conditions, engine roughness may occur before peak EGT is reached. In this case, continue to lean until 4-18 1 October 1978 CESSNA MODEL TR182 SECTION 4 NORMAL PROCEDURES MIXTURE EXHAUST GAS DESCRIPTION TEMPERATURE RECOMMENDED LEAN (Pilot's Operating Handbook 500F Rich of Peak EGT and Power Computer) BEST ECONOMY Peak EGT Figure 4-4. EGT Table peak EGT is established, then enrichen to any desired mixture setting that allows smooth engine operation. The mixture may be leaned during descent to provide smooth engine operation and improved fuel economy. Any change in altitude, power or carburetor heat will require a change in the mixture setting and a recheck of the EGT. Carburetor ice, as evidenced by an unexplained drop in manifold pressure, can be removed by application of full carburetor heat. Upon regaining the original manifold pressure indication (with heat off),use the minimum amount of heat (by trial and error) to prevent ice from forming. When operating above approximately 5000 feet at maximum recommended cruise power, the heat available from turbocharging increases with altitude and carburetor icing becomes less likely. Carburetor heat may be used an an alternate air source in the event the induction air filter becomes blocked. However, since application of full carburetor heat at high altitudes may result in the loss of as much as 10 inches of manifold pressure, carburetor heat should be used only as necessary. With carburetor heat on, throttle and mixture should be readjusted as necessary. STALLS The stall characteristics are conventional and aural warning is provided by a stall warning horn which sounds between 5 and 10knots above the stall in all configurations. Altitude loss during stall recovery may be as much as 300 feet. Power-off stall speeds at maximum weight for both forward and aft C.G. positions are presented in Section 5. 1 October 1978 4-19 SECTION 4 NORMAL PROCEDURES CESSNA MODEL TR182 BEFORE LANDING In view of the relatively low drag of the extended landing gear and the high allowable gear operating speed (140 KIAS), the landing gear should be extended before entering the traffic pattern. This practice will allow more time to confirm that the landing gear is down and locked. As a further precaution, leave the landing gear extended in go-around procedures or traffic patterns for touch-and-go landings. Landing gear extension can be detected by illumination of the gear down indicator light (green), absence of a gear warning horn with the throttle retarded below approximately 12 inches of manifold pressure and! or the wing flaps extended beyond 25°, and visual inspection of the main gear position. Should the gear indicator light fail to illuminate, the light should be checked for a burned-out bulb by pushing to test. A burned- out bulb can be replaced in flight with the landing gear up (amber) indicator light. LANDING NORMAL LANDING Landings should be made on the main wheels first to reduce the landing speed and the subsequent need for braking in the landing roll. The nose wheel is lowered gently to the runway after the spaad hag diminished to avoid unnecessary nose gear load. This procedure is especially impor- tant in rough field landings. SHORT FIELD LANDING For a short field landing, make a power-off approach at 64 KIAS with 40° flaps and land on the main wheels first. Immediately after touchdown, lower the nose gear to the ground and apply heavy braking as required. For maximum brake effectiveness after all three wheels are on the ground, retract the flaps, hold full nose up elevator and apply maximum possible brake pressure without sliding the tires. CROSSWIND LANDING When landing in a strong crosswind, use the minimum flap setting required for the field length. Although the crab or combination method of drift correction may be used, the wing-low method gives the best control. After touchdown, hold a straight course with the steerable nose wheel and occasional braking if necessary. 4-20 1 October 1978 CESSNA MODEL TR182 SECTION 4 NORMAL PROCEDURES BALKED LANDING In a balked landing (go-around) climb, the wing flap setting should be reduced to 20° immediately after full power is applied. After all obstacles are cleared and a safe altitude and airspeed are obtained, the wing flaps should be retracted. To prevent overboosting the engine, power should then be reduced to approximately 25 inches of manifold pressure and the carburetor heat control placed in the cold position. COLD WEATHER OPERATION STARTING Prior to starting on cold mornings, it is advisable to pull the propeller through several times by hand to "break loose" or "limber" the oil, thus conserving battery energy. NOTE When pulling the propeller through by hand, treat it as if the ignition switch is turned on. A loose or broken ground wire on either magneto could cause the engine to fire. In extremely cold (-18°C and lower) weather, the use of an external pre- heater and an external power source are recommended whenever possible to obtain positive starting and to reduce wear and abuse to the engine and the electrical system. Pre-heat will thaw the oil trapped in the oil cooler, which probably will be congealed prior to starting in extremely cold temperatures. When using an external power source, the position of the master switch is important. Refer to Section 9, Supplements, for Ground Service Plug Receptacle operating details. Cold weather starting procedures are as follows: With Preheat: 1. With ignition switch turned off, mixture full rich and throttle closed, prime the engine one to two strokes. NOTE Use heavy strokes of the primer for best atomization of fuel. After priming, push primer all the way in and turn to the locked position to avoid the possibility of the engine drawing fuel through the primer. 1 October 1978 4-21 SECTION 4 NORMAL PROCEDURES CESSNA MODEL TR182 2. Propeller -- CLEAR. 3. Avionics Power Switch -- OFF. 4. Master Switch -- ON. 5. Throttle -- CLOSED until engine starts. 6. Ignition Switch -- START (release to BOTH when engine starts). Without Preheat: 1. Prime the engine two to four strokes with mixture full rich and throttle closed. 2. Propeller -- CLEAR. 3. Avionics Power Switch -- OFF. 4. Master Switch -- ON. 5. Throttle -- CLOSED until engine starts. 6. Ignition Switch -- START. 7. Release ignition switch to BOTH when engine starts. 8. Oil Pressure -- CHECK. 9. Primer -- LOCK. NOTE If the engine does not start during the first few attempts, or if engine firing diminishes in strength, it is probable that the spark plugs have been frosted over. Preheat must be used before another start is attempted. NOTE Pumping of the throttle will make starting more difficult due to a rapidly varying mixture. The carburetor is not equipped w it.h an accelerator pump. OPERATION During cold weather operations, no indication will be apparent on the oil temperature gage prior to takeoff if outside air temperatures are very cold. After a suitable warm-up period (2 to 5 minutes at 1000 RPM), smoothly accelerate the engine several times to higher engine RPM. If the engine accelerates smoothly and the oil pressure remains normal and steady, the airplane is ready for takeoff. Rough engine operation in cold weather can be caused by a combina- tion of an inherently leaner mixture due to the dense air and poor vaporization and distribution of the fuel-air mixture to the cylinders. The effects of these conditions are especially noticeable during operation on one magneto in ground checks wh er-e only one spark plug fires in each cylinder. 4-22 1October 1978 CESSNA MODELTR182 SECTION 4 NORMALPROCEDURES For optimum operation of the engine in cold weather, the appropriate use of carburetor heat may be necessary. The following procedures are indicated as a guideline: 1. Use the minimum carburetor heat required for smooth operation in takeoff, climb, and cruise. NOTE Care should be exercised when using partial carburetor heat to avoid icing. Partial heat may raise the carburetor air temperature to 0° to 21°Crange where icing is critical under certain atmospheric conditions. 2. The carburetor air temperature gage can be used as a reference in maintaining carburetor air temperature at or slightly above the top of the yellow arc by application of carburetor heat. HOT WEATHER OPERATION The general warm temperature starting information in this section is appropriate. Avoid prolonged engine operation on the ground. NOISE ABATEMENT Increased emphasis on improving the quality of our environment requires renewed effort on the part of all pilots to minimize the effect of airplane noise on the public. We, as pilots, can demonstrate our concern for environmental improvement, by application of the following suggested procedures, and thereby tend to build public support for aviation: 1. Pilots operating aircraft under VFR over outdoor assemblies of persons, recreational and park areas, and other noise-sensitive areas should make every effort to fly not less than 2000feet above the surface, weather permitting, even though flight at a lower level may be consistent with the provisions of government regulations. 2. During departure from or approach to an airport, climb after takeoff and descent for landing should be made so as to avoid prolonged flight at low altitude near noise-sensitive areas. 1 October 1978 4-23 SECTION 4 NORMAL PROCEDURES CESSNA MODEL TR182 NOTE The above recommended procedures do not apply where they would conflict with Air Traffic Control clearances or instructions, or where, in the pilot's judgment, an altitude of less than 2000 feet is necessary for him to adequately exercise his duty to see and avoid other aircraft. The certificated noise level for the Model TR182 at 3100 pounds maximum weight is 72.5 dB(A). No determination has been made by the Federal Aviation Administration that the noise levels of this airplane are or should be acceptable or unacceptable for operation at, into, or out of, any airport. 4-24 1 October 1978 CESSNA MODEL TR182 SECTION 5 PERFORMANCE SECTION 5 PERFORMANCE TABLE OF CONTENTS Page Introduction . . . . . . . Use Of Performance Charts Sample Problem . Takeoff Cruise .... Fuel Required Landing ... Demonstrated Operating Temperature . Figure 5-1, Airspeed Calibration - Normal Static Source Airspeed Calibration - Alternate Static Source Figure 5-2, Temperature Conversion Chart Figure 5-3, Stall Speeds . Figure 5-4, Takeoff Distance - 3100 Lbs . Takeoff Distance - 2800 Lbs And 2500 Lbs Figure 5-5, Rate Of Climb - Maximum . . . . . Figure 5-6, Time, Fuel, And Distance To Clim.b - Maximum Rate Of Climb .... Time, Fuel, And Distance To Climb - Norrnal Climb . . . . . . Figure 5-7, Cruise Performance - 2000 Feet Cruise Performance - 4000 Feet Cruise Performance - 6000 Feet Cruise Performance - 8000 Feet Cruise Perform.ance - 10,000Feet Cruise Performance - 12,000Feet Cruise Performance - 14,000Feet Cruise Performance - 16,000Feet Cruise Performance - 18,000Feet Cruise Performance - 20,000Feet Figure 5-8, Range Profile . . Figure 5-9, Endurance Profile Figure 5-10, Landing Distance 5-3 5-3 5-3 5-4 5-5 5-5 5e7 5-7 5-8 5-9 5-10 5-11 5-12 5-13 5-14 5-15 5-16 5-17 5-18 5-19 5-20 5-21 5-22 5-23 5-24 5-25 5-26 5-27 5-28 5-29 1 October 1978 5-1/(5-2 blank) , CESSNA MODELTR182 SECTION 5 PERFORMANCE INTRODUCTION Performance data charts on the following pages are presented so that you may know what to expect from the airplane under various conditions, and also, to facilitate the planning of flights in detail and with reasonable accuracy. The data in the charts has been computed from actual flight tests with the airplane and engine in good condition and using average piloting techniques. It should be noted that the performance information presented in the range and endurance profile charts allows for 45 minutes reserve fuel based on 45%power. Fuel flow data for cruise is based on the recommended lean mixture setting. Some indeterminate variables such as mixture leaning technique, fuel metering characteristics, engine and propeller condition, and air turbulence may account for variations of 10%or more in range and endurance. Therefore, it is important to utilize all available information to estimate the fuel required for the particular flight. USE OF PERFORMANCE CHARTS Performance data is presented in tabular or graphical form to illus- trate the effect of different variables. Sufficiently detailed information is provided in the tables so that conservative values can be selected and used to determine the particular performance figure with reasonable accuracy. SAMPLE PROBLEM The following sample flight problem utilizes information from the various charts to determine the predicted performance data for a typical flight. The following information is known: AIRPLANE CONFIGURATION Takeoff weight Usable fuel 3050 Pounds 88 Gallons TAKEOFF CONDITIONS Field pressure altitude Temperature Wind component along runway Field length 3500Feet 24°C (16°C above standard) 12 Knot Headwind 3500Feet 1 October 1978 5-3 SECTION 5 PERFORMANCE CESSNA MODELTR182 CRUISE CONDITIONS Total distance Pressure altitude Temperature Expected wind enroute 810 Nautical Miles 11,500Feet 8°C 10 Knot Headwind LANDING CONDITIONS Field pressure altitude Temperature Field length 3000Feet 25°C 3000Feet TAKEOFF The takeoff distance chart, figure 5-4, should be consulted. keeping in mind that the distances shown are based On the short field technique. Conservative distances can be established by reading the chart at the next higher value of weight, altitude and temperature. For example, in this particular sample problem, the takeoff distance information presented for a weight of 3100pounds, pressure altitude of 4000feet and a temperature of 30°C should be used and results in the following: Ground roll Total distance to clear a 50-foot obstacle 1215Feet 2310 Feet These distances are well within the available takeoff field length. How- ever, a correction for the effect of wind may be made based on Note 2 of the takeoff chart. The correction for a 12 knot headwind is: i~ Knots 9 Knots x 10% = 13% Decrease This results in the following distances, corrected for wind: Ground roll, zero wind Decrease in ground roll (1215feet x 13%) Corrected ground roll 1215 158 1057Feet Total distance to clear a 50-foot obstacle. zero wind Decrease in total distance (2310feet x 13%) Corrected total distance to clear a 50-foot obstacle 2310 300 2010 Feet 5-4 1 October 1978 CESSNA MODEL TR182 SECTION 5 PERFORMANCE CRUISE The cruising altitude should be selected based on a consideration of trip length, winds aloft, and the airplane's performance. A cruising altitude and the expected wind enroute have been given for this sample problem. However, the power setting selection for cruise must be deter- mined based on several considerations. These include the cruise perfor- mance characteristics presented in figure 5-7, the range profile chart presented in figure 5-8,and the endurance profile chart